Coupling for suspended load control apparatus, system, and method

ABSTRACT

Disclosed are systems, apparatuses, and methods for a suspended load control system for use on or with respect to a main load bearing line, carrier hook, and or head block of a crane.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a non-provisional of and claims the benefit of andincorporates by reference U.S. provisional patent application62/940,155, filed Nov. 25, 2019, and titled, “SUSPENDED LOAD CONTROLCRANE HOOK APPARATUS, SYSTEM, AND METHOD” and is a continuation-in-partof, incorporates by this reference, and claims the benefit of U.S.patent application Ser. No. 16/988,373, filed Aug. 7, 2020 and titled,“SUSPENDED LOAD STABILITY SYSTEMS AND METHODS”, which application is acontinuation of Patent Cooperation Treaty patent application numberPCT/US19/13603, filed Jan. 15, 2019, which application claims thebenefit of and incorporates by reference U.S. provisional patentapplication 62/627,920, filed Feb. 8, 2018 and titled “SUSPENDED LOADSTABILITY SYSTEM THROUGH SELF POWERED AUTOMATED ELECTRIC DUCT FANCONTROL”, and U.S. provisional patent application No. 62/757,414, filedon Nov. 8, 2018, titled “LOAD STABILITY SYSTEM FOR SUSPENDED LOADCHAOTIC MOTION.

FIELD

This disclosure is directed to improved apparatus(es), system(s), andmethod(s) for and related to control of loads suspended on a suspensioncable by a hook below a carrier.

BACKGROUND

People and/or equipment (“loads”) may be transported to or from alocation as a load suspended by a cable from a helicopter, crane,airplane, or other carrier using a hoist system. Cranes, helicopters,and aircraft (including fixed-wing aircraft) may be referred tocollectively herein as “carriers”. Carriers with a connection to theground or to another platform (such as a platform floating on water),such as cranes, may be referred to herein as “platform-based carriers”.Carriers other than platform-based carriers, such as helicopters andaircraft (fixed wing or otherwise), may be referred to herein as “flyingcarriers”.

A hook or similar structure may be found on the bottom of a suspensioncable; the load may be secured to the hook. The hook may transfer alifting force between the carrier and the load. The hook may comprise orbe part of an assembly which includes a block; the block maywithstanding impact and protecting the hook from contact with theenvironment.

During operations in which a load is transported by a carrier, the loadmay be subject to winds, interaction with the suspension cable, andother external and internal factors that may cause the load to move inan unstable, undesirable, or hazardous manner. To address suchconditions, and to otherwise control a suspended load, operators ofcarriers may want to use equipment that provides control of a suspendedload, including equipment that provides suspended load control remotefrom the carrier, e.g. at or near a load, such as using remotely poweredfans. Other systems have been developed to provide suspended loadcontrol below platform-based carriers by changing the orientation of aspinning gyroscope or flywheel, though these systems may have adifferent type of control system, may be able to output torque but nothorizontal thrust, and may not be suitable for use below a flyingcarrier due to weight.

In hoist and sling operations, it may be desirable for the load to hangdirectly off of a hook, rather than off of equipment to provide controlof a suspended load. This may be because the hook is very sturdy, hasvery few parts, and single-purpose. For example, and as noted, the hookmay transfer a lifting force between the carrier and the load; thelifting force may be very large. In contrast, equipment to providecontrol of a suspended load may include many parts, e.g. fans, etc., andmay be more subject to damage and failure. Operators of carriers may bereluctant or unable to suspend a load directly from equipment to providecontrol of a suspended load, but may prefer or may need to continue tosuspend the load from a hook and or block.

In addition, in hoist and sling operations, the suspension cable isoften a braided steel cable, or the like. Suspension cables, whetherbraided or not, should not be subject to torque, as this may cause thecable to wind up, unwind, kink, weaken, break, not wind properly onto awinch, or the like.

In hoist and sling operations, observed motion of suspended loadsincludes the following components: vertical translation (motion up anddown) along the Y axis (referred to herein as “vertical translation”);horizontal translation along either or both the X and Z axis; androtation or “yaw” about the Y axis. Horizontal translation can manifestas lateral motion or, when in both the X and Z axis, as conical pendulummotion of the load, with the pivot point of the pendulum being where thecable is secured to the carrier (“pendular motion”); pendular motiongenerally also includes a component of vertical translation. Roll(rotation about the X axis) and pitch (rotation about the Y axis) mayalso occur, though if a load is suspended by a cable and is not buoyant,the dominant motions are vertical translation, horizontal translation,pendular motion, and yaw. Vertical and horizontal translation may becaused by movement of the suspension cable, such as by movement of thecarrier, movement of the load, differences in momentum between the loadand the carrier, by wind—including propeller wash—impacts, by lettingout or retracting cable from or to a hoist, and by external forces.Axis, when discussed herein, are relative to a normal axis of asuspended load, a normal axis of a carrier, or a normal axis of agravitational field.

Yaw, lateral motion, and pendular motion complicate lift operations,cause delays, and can lead to death of aircrew, crane operators, and ofpeople on the ground. Yaw and lateral and pendular motion can alsointerfere with bringing a load into or delivering a load to a location.For example, ground crew may not be able to approach a load if it isundergoing pendular motion or yaw or a platform-based carrier operatormay not be able to completely lower a load to a desired destination ifthe load is undergoing pendular motion or yaw. For example, delivery ofa load to a deck of a ship or to a worksite may be significantlycomplicated by pendular motion or yaw of the load, even if the deck orworksite is stable and is not also subject to heave, roll, or pitch, asit may be.

One or more components of undesired motion of the load may accelerate orgrow more pronounced as a load is drawn up to the carrier and thesuspension cable shortens. Horizontal and pendular motion of a load canalso interact with the carrier to produce dangerous reactive orsympathetic motion in the carrier.

Therefore, there is a need for equipment to provide control of asuspended load, such as to provide torque or a horizontal force tocontrol yaw, lateral motion, and pendular motion, wherein the equipmentto provide control of the suspended load can work in conjunction with ahook and or block.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a view of a carrier, carrier hook, and suspended load controlsystem (“SLCS”), in accordance with an embodiment.

FIG. 2 is the carrier hook and SLCS of FIG. 1, partially exploded, inaccordance with an embodiment.

FIG. 3 is a portion of the carrier hook and SLCS of FIG. 1, inaccordance with an embodiment.

FIG. 4 is an exploded view of portions of the carrier hook and SLCS ofFIG. 1, in accordance with an embodiment.

FIG. 5A is a detail of a winch bracket, in accordance with anembodiment.

FIG. 5B is a detail of a winch bracket, a winch, and a portion of a fanunit, in accordance with an embodiment.

FIG. 6 is a detail of a winch and control line, in accordance with anembodiment.

FIG. 7A is a fan unit bracket, in accordance with an embodiment.

FIG. 7B is a detail of a control system rotational coupling, fan unitbracket, fan unit, and electronics box, in accordance with anembodiment.

FIG. 8 is a fan unit bracket and electronics box, in accordance with anembodiment.

FIG. 9A is a fan unit, in accordance with an embodiment.

FIG. 9B is the fan unit of FIG. 9A with vertical cross-section through acenter line, in accordance with an embodiment.

FIG. 10 is the fan unit of FIG. 9A with vertical cross-section inelevation view, in accordance with an embodiment.

FIG. 11 is a top plan view of a carrier hook and SLCS, in accordancewith an embodiment.

FIG. 12 is a carrier hook, SLCS, and remote pendant, in accordance withan embodiment.

FIG. 13A is a back elevation view of the remote pendant, in accordancewith an embodiment.

FIG. 13B is an oblique view of the remote pendant, in accordance with anembodiment.

FIG. 13C is a front elevation view of the remote pendant, in accordancewith an embodiment.

FIG. 14 schematically illustrates operational components of a suspendedload control system including a remote pendant interface in accordancewith one embodiment.

FIG. 15 illustrates an operational routine of a suspended load controlsystem including multiple modes or command states in accordance with oneembodiment.

FIG. 16 illustrates a decision and control routine of a suspended loadcontrol system in accordance with one embodiment.

FIG. 17A illustrates a graph of response of a suspended load tocontrolled by a suspended load control system, with inadequate tensionon control lines.

FIG. 17B illustrates a graph of response of a suspended load tocontrolled by a suspended load control system, with adequate tension oncontrol lines.

DETAILED DESCRIPTION

Reference is now made in detail to the description of the embodimentsillustrated in the drawings. While embodiments are described inconnection with the drawings and related descriptions, there is nointent to limit the scope to the embodiments disclosed herein. On thecontrary, the intent is to cover all alternatives, modifications andequivalents. In alternate embodiments, additional devices, orcombinations of illustrated devices, may be added to, or combined,without limiting the scope to the embodiments disclosed herein. Forexample, the embodiments set forth below are primarily described in thecontext of a helicopter sling load, search and rescue operations, and/orcrane operations. However, these embodiments are illustrative examplesand in no way limit the disclosed technology to any particularapplication or platform.

The phrases “in one embodiment,” “in various embodiments,” “in someembodiments,” and the like are used repeatedly. Such phrases do notnecessarily refer to the same embodiment. The terms “comprising,”“having,” and “including” are synonymous, unless the context dictatesotherwise. As used in this specification and the appended claims, thesingular forms “a,” “an,” and “the” include plural referents unless thecontent clearly dictates otherwise. It should also be noted that theterm “or” is generally employed in its sense including “and/or” unlessthe content clearly dictates otherwise. When an element in a figure islabeled with a number which includes a letter, instances of the elementare generally similar and a group of such elements may be referred totogether or collectively, without the letter.

Platform-based carrier operators may move loads at slow rates tominimize pendular motion or may use dedicated control cables (whether onthe ground, neighboring structures, or to or from the carrier). However,these measures increase costs, complexity, and risk of failure of asuspended load operation. These measures are inadequate and highlyproblematic.

In various embodiments, as described further herein, a suspended loadcontrol system addresses control of a load, independent from a carrier.The suspended load control system or suspended load stability system(referred to together as, “SLCS”) of this disclosure controls a load byexerting or outputting force or force vectors from thrusters, fans,propellers, flywheels, gyroscopes, or the like at, or near, a locationof the load. Thrusters, fans, propellers and electric ducted fans may bereferred to herein as “EDFs” or “fans”. Vector thrust force produced bythe fans and or winches may be used to counteract yaw and pendularmotion. Vector thrust force produced by the fans may be used totranslate a load horizontally, such as to avoid an obstacle or to move aload into an offset position relative to a normal lowest-energy hangingposition. Vector thrust force produced by the fans and or winches may beused to control the fine location and rotation of a load, independentlyfrom the carrier. Vector thrust force produced by the fans may be usedto increase the speed of operation of a carrier while maintaining safeoperating parameters.

The SLCS of this disclosure further may be mounted on a hook and orblock. The SLCS may be mounted on the hook and or block via a rotationalcoupling, wherein the rotational coupling comprises one or morebearings. The rotational coupling may allow the SLCS to rotate withoutimparting significant torque on the main load bearing line.

The SLCS of this disclosure may further comprise one or more winches;the winches may be secured to the load with one or more winch controllines. A control module of the SLCS may control the winch to maintaintension on the winch control lines; the control module may furthercontrol thrusters of the SLCS to control the load.

Consequently, an SLCS as disclosed herein works with or in conjunctionwith existing hooks and or blocks, enhances safety, improves performanceof carrier and load operations, and may allow carrier operators toincrease work output and to reduce damage to loads and surroundingobjects, as the SLCS dynamically controls fine location and rotation ofa load. An SLCS can provide benefits to, for example, platform-basedcarrier operations and to flying carrier operations.

Once deployed and in-use, the SLCS is agnostic with respect to theplatform from which the load is suspended (e.g., the characteristics ofa crane or helicopter “ownship”, etc.), as it independently determinesits state, tensions a control line between a winch and the load, and oras it independently applies thrust to stabilize the load or to directthe load in a desired direction, without imparting significant torque onthe main load bearing line. This permits widespread adoption of thesystem regardless of carrier type, lowering cost and mitigating solutionrisks.

FIG. 1 illustrates an embodiment of a suspended load control carrierhook system and load 100 in which platform-based carrier 124 supportsand or relocates load 130 via main load bearing line 125 and loadbearing connector lines 115A through 115E. Platform-based carrier 124 isillustrated as an example, a flying carrier may also or alternatively beused.

With reference to FIG. 1 through FIG. 4, carrier 124 may support load130 by way of a winch, hoist or the like in carrier 124, a suspensioncable (also referred to herein as a “main load bearing line 125”), ahead block 145, which is secured to the main load bearing line 125, ahead block hook 150, and one or more load bearing connector lines 115,which secure load 130 to head block hook 150. In the example illustratedin FIG. 1, load bearing connector line 115A may branch into a pluralityof connector lines 115B through 115E (referred to together withconnector line 115 as connector line or lines 115). Connector lines 115may be secured to head block hook 150 (see FIG. 2) via one or more loadbearing rotational coupling(s) 122A, 122B, or 122C which allow load 130to rotate, spin, or undergo yaw without winding up or unwinding mainload bearing line 125. Load bearing rotational coupling 122 maycomprise, for example, thrust bearings or another bearing set or bearingsystem. In the embodiment illustrated in FIG. 1, SLCS 105 includes fourcontrol lines 110A through 110D (referred to collectively as controllines 110). A different number of control lines could be used, such asone, two, three, or more than four. Main load bearing line 125 is oftena cable, including a braided cable. Rotation of main load bearing line125 around the Y axis may not be desirable. For example, a braided cablemay unwind or may develop over-winding kinks if is rotated, either ofwhich can result in problems that range from delays in work, to damage,to catastrophic failure of equipment, including of the main load bearingline, hoist, or the like. To address this issue, load bearing rotationalcoupling 122A, 122B, and or 122C may be located between the load 130 andat least one of hook 150 and or head block 145; however, the loadbearing rotational coupling may also allow load 130 to rotate in anuncontrolled manner, which, as noted, may be undesirable.

SLCS 105 may be secured to head block 145, which may allow SLCS 105 tobe used with respect to a wide range of existing crane equipment.However, if SLCS 105 is imparting force on load 130, per the remarksabove, SLCS 105 should not also impart rotational force or torque on themain load bearing line. To address this, SLCS 105 is secured to headblock 145 at, by, or in conjunction with control system rotationalcoupling 120 (please see FIG. 2). Control system rotational coupling 120may be, for example, a thrust bearing set, a tapered roller thrustbearing set, a spherical roller thrust bearing set, or the like. Controlsystem rotational coupling 120 may not bear or transfer a main liftingforce between carrier 124 and load 130; control system rotationalcoupling 120 may only bear the weight of SLCS 105 and of tension oncontrol lines 110.

As noted, SLCS 105 is secured to load 130 by one or more control lines110, wherein the control lines 110 secure winches 195 (labeled in FIG.4, FIG. 5A, FIG. 5B, and FIG. 6) to load 130. Winches 195 may be used bySLCS 105 to at least one of i) detect slack in control lines 110 and orii) to produce and or maintain tension on control lines 110. SLCS 105may produce and or maintain tension on control lines 110 to transferforce, such as torque, from SLCS 105 and from one or more fan units 155of SLCS 105, to load 130. Without tension on control lines 110, theability of SLCS 105 to react to movement of and to control load 130 maybe severely compromised and or may be delayed. Delay in reaction timebetween SLCS 105 and load 130 may severely hinder ability of SCLS 105 totransfer force to load 130. Thus maintaining tension on control lines110 may effect the ability of SLCS 105 to control load 130, on power useby SLCS 105, on battery life of SLCS 105, and on mission objectives.

To develop force to be transferred to load 130, SLCS 105, SLCS 105 mayuse thrust from, for example, fan units 155. Fan units 155 may beopposite each other, on two or more sides of SLCS 105. As illustrated inthese examples, each fan unit 155 comprises two EDFs generally orientedopposite one another. Thrust from EDFs in fan units 155, as well aswinches 195 and tension on control lines 110, may be used by operationalcomponents of SLCS 105 discussed in relation to FIG. 14, operationalroutine(s) of SLCS 105 discussed in relation to FIG. 15, and decisionand control routine of SLCS 105 discussed in relation to FIG. 16, tocontrol or influence load 130. Alternative to fan units 155, SLCS 105may comprise one or more flywheels; an acceleration of flywheels and orchange in orientation of a spinning flywheel may impart torque on SLCS105, which torque may be transferred to load 130 with winches 195 andcontrol lines 110.

FIG. 2 illustrates an embodiment of carrier hook and SLCS 105 of FIG. 1,partially exploded, in accordance with an embodiment. In addition toelements called out and described in relation to FIG. 1, called out arehead block 145, head block hook 150, control system rotational coupling120, fan unit 155A and fan unit 155B, control line-load securement(s)140, and load bearing connector line-load securement(s) 135. A view withmore detail of certain of these components is also provided in FIG. 4.

FIG. 3 illustrates an embodiment of a portion of carrier hook and SLCS105 of FIG. 1, in accordance with an embodiment. In FIG. 3, illustratedand labeled elements comprise the following: one or more control line110A-110D, which may extend down to load 130 (in embodiments, adifferent number of control lines may be used); load bearing connectorline(s) 115 (in embodiments, a different number of load bearingconnector lines may be used); head block hook 150; head block 145(which, in combination with head block hook 150 may also be referred toas a “carrier hook”); control system rotational coupling 120; fan unit155A and fan unit 155B; fan electronics conduit 170; electronics box165A and electronics box 165B; main power conduit 180; main power feederconduit 175; and main load bearing line 125. Electronics box 165A andelectronics box 165B may contain electronics, computers, and algorithmsor modules and other operational components discussed in relation toFIGS. 14 to 16. Main power conduit 180 may extend up to carrier 124 andprovide power, such as electrical power, to SLCS 105 from a power sourcein carrier 124. In addition or alternatively, SLCS 105 may comprisebattery packs to provide some or all power to SLCS 105. In addition toproviding power, main power conduit 180 or another conduit may relaycontrol and or sensor signals between SLCS 105 and other sources ordestinations of control and or sensor signals. As noted, main loadbearing line 125 may extend up to carrier 124, such as to a hoist ofcarrier 124.

FIG. 4 illustrates an exploded detail of an embodiment of a portion ofcarrier hook and SLCS 105 of FIG. 1. Illustrated and labeled elementscomprise the following: control system rotational coupling 120. Controlsystem rotational coupling 120 carries fan units 155, electronics box165, winch bracket 190A and 190B, which may secure winches 195A through195D to fan unit 155A and 155B and which may hold electronics box 165(electronic box 165 may be located in a different location, such as onfan unit 155); winches 195A through 195D. Control system rotationalcoupling 120 allows SLCS to rotate separately from head block 145,without imparting significant torque on head block 145 or main loadbearing line 125, e.g. where only friction in control system rotationalcoupling 120 would transfer torque from SLCS 105 to head block 145,wherein such friction-based torque transfer would be relativelyinsignificant and less than a capacity of main load bearing line 125 toabsorb and resist torque. Control system rotational coupling-head blocksecurements 200 are one or more securement structures, such as bolts,which to secure control system rotational coupling 120 to head block145.

FIG. 5A illustrates an embodiment of winch bracket 190, which may securewinch 195 to fan unit 155 and, via fan unit bracket 185, to controlsystem rotational coupling 120 and, thereby, to head block 145. Winch195 may be secured to control system rotational coupling 120 via otherstructures, such as to fan unit bracket 185 and or another dedicatedstructure.

FIG. 5B illustrates an embodiment of winch bracket 190 and winch 195. Incombination with operational components and modules of a suspended loadcontrol system discussed in relation to FIGS. 14 to 16, winch 195 ordata from winch 195 may be used to sense an amount of strain or tensionon one or more control line(s) 110. Operational components and modulesof a suspended load control system discussed in relation to FIGS. 14 to16 may use winch 195 to draw tension on one or more control line(s) 110.Sensed tension or lack of tension on control line(s) 110 may indicateand or may be produced by desired or undesired motion of load 130.Tension may be imparted on control line(s) 110 by winch 195 to impartforce on load 130; such force may be communicated between winch 195 and,for example, fan unit 155, such as when one or more fan unit 155 isoperating to provide a force, and or on head block 145, which may causea center of gravity of load 130 to bias in a direction relative to headblock 145 and main load bearing line 125.

FIG. 6 illustrates an embodiment of winch bracket 190, winch 195, andcontrol line 110 extending from winch 195. More than one control line110 or control line feeder lines may extend from winch 195. Winchbracket 190 may place winch 195 distal relative to a central verticalaxis (or Y axis) of main load bearing line 125. As noted, winch brackets190 and winches 195 may be symmetrical about the central vertical axis(or Y axis) of main load bearing line 125. In embodiments, a greater orlesser number of winches 195 and or winch bracket 190 may be used. Winch195 may comprise one or more tension sensor to sense tension on winch195 from control line 110. A tension sensor may comprise, for example, aposition encoder, a torque sensor, a stain gauge, a spring-loaded andinstrument guide for control line 110, and the like. Winch 195 mayfurther comprise, or incorporate into a tension sensor, sensors todetect and report an amount of control line 110 which has been payed outof or into winch 195.

FIG. 7A illustrates an embodiment of fan unit bracket 185, which maysecure fan unit 155 to control system rotational coupling 120, such as,for example, via bolts, welding, straps, or the like. In embodiments,other components may be intermediate between fan unit 155 and controlsystem rotational coupling 120.

FIG. 7B illustrates an embodiment of control system rotational coupling120 secured to fan unit bracket 185, fan unit 155, and electronics box165.

FIG. 8 illustrates an embodiment of electronics box 165 secured to fanunit bracket 185. In this embodiment, electronics box 165 comprisescontrol system antenna 205. Control system antenna 205 may allowwireless communication, such as with remote pendant 235 and or withcomponents in carrier 124, and or with wireless sensors, sensor input,or sensor output, such as with respect to GPS, LIDAR, RADAR, SONAR,image (visible, infrared, etc. camera), acoustic (microphone), inertial,gyroscopic sensors and the like.

In an embodiment, electronics box 165 may comprise, for example, powersupply system, power regulators, relays, buffers, or the like, toprovide regulated power to a fan unit. In an embodiment, electronics box165 may comprise batteries. In an embodiment, electronics box 165 maycomprise, for example, electronic speed controllers, motor drivers, andthe like, to control electrical power to a fan unit.

In an embodiment, electronics box 165 may comprise, for example,operational components (e.g. computer processor and memory), operationalroutine, and a decision and control routine of a suspended load controlsystem, discussed in relation to FIGS. 14 to 16.

FIG. 9 illustrates an embodiment of fan unit 155, in which fan unit 155comprises the following: fan unit outlet cover 210, which may discourageingress of debris into fan unit 155 and which allows air or anotherthrust fluid to exit fan unit 155; fan inlet 220, which may discourageingress of debris into fan unit 155 and may allow air or another thrustfluid to enter fan unit 155; and fan 215A and fan 215B. Fan 215A and fan215B may be ducted fans. Fan 215A and fan 215B may be driven by electricmotor(s), with electricity obtained from a battery pack, such as abatter pack in electronics box 165 and or from carrier 124 and providedto fan 215A and or fan 215B by electronics box 165 through fanelectronics conduit 170, potentially in conjunction with control signalsand or potential in conjunction with generation of control signals, suchas electromagnetic frequency (EMF) and or encoder feedback from electricmotors in fan 215.

FIG. 10 illustrates an embodiment of fan unit 155, including fan inlet220, fan 215A and fan 215B. Fan 215A and fan 215B may be oriented 180degrees opposite one another, such that each produce thrust opposite theother. Fan 215A and fan 215B may be oriented other than 180 degreesopposite one another.

Fan units 155 may comprise a cowl which protects one or more fan(s). Thecowl may be hardened, to withstand impact with the environment. The cowlunit may be made of metal, plastics, composite materials, includingfiber reinforced resin, and the like. The fan in fan unit 155 maycomprise blades and motor(s), such as electric motor(s). The electricmotors within a fan may be sealed against dust, sand, water, and debris.

Fans in each fan unit propel thrust fluid (such as air) in fixeddirections, such as fixed directions opposite each other; e.g. offset by180 degrees. In other embodiments, a fewer or greater number of fanunits and/or fans may be used. In other embodiments, the fan unitsand/or fans may be aligned other than as illustrated, e.g., offset bygreater or fewer than 180 degrees, with or without offset along other ofthe axis. A mechanical steering component may be included (notillustrated) to dynamically reposition a fan unit and/or fan within afan unit.

Fans in individual of the fan units 155 may be activated separately,with different power, to produce thrust vectoring or thrust vectorcontrol of an assembly of fans, such as of SLCS 105. For example, toproduce clockwise yaw (with directions relative to FIG. 11), a fan infan unit 155B may be activated by itself or in conjunction with anopposing fan on an opposite side of fan unit 155A to produce torque. Toproduce lateral translation forces on SLCS 105 and load 130, fans on asame side of fan unit 155A and 155B may be activated. Simultaneouslateral translation and rotation may be produced.

FIG. 11 illustrates an embodiment of SLCS 105 in which thrust vector(s)230A through 230D may be produced by fan units 155A and 155B. Thrustvector(s) 230A through 230D may be controlled by, for example,operational components of a suspended load control system discussed inFIGS. 14 to 16 to produce, for example rotational force(s) 225 (e.g. yawforces or torque) or translational forces (e.g. forces along one or bothX and Z axis) which may be transmitted between SLCS 105 and load 130 byone or more of control line(s) 110. Lifting and translational forcesfrom carrier 124 may be transmitted to load by one or more load bearingconnector line(s) 115.

FIG. 12 illustrates an embodiment of SLCS and load 100 in wirelesscommunication with remote pendant 235. Remote pedant 235 may provide andor relay control signals and or sensor information between SLCS 105,remote pendant 235, a user, or other sources or destinations, such assystems in a carrier. Other sources or destinations may be in wirelessor wireline communication with one or both of SLCS 105 and remotependant 235.

FIG. 13A illustrates an embodiment of remote pendant 235 comprising, forexample, activation controller 240. FIG. 13B illustrates another view ofan embodiment of remote pendant 235. FIG. 13C illustrates another viewof an embodiment of remote pendant 235 comprising, for example, on/offswitch 245, state selector 250, and manual/rotational control 251.On/off switch 245 may be used to turn on remote pendant 235. Stateselector 250 may be used to select a command state of SLCS 105, as maybe discussed in relation to FIG. 15. Activation controller 240 may beused to activate or deactivate SLCS 105 in or relative to a selectedcommand state. Manual/rotational control 251 may be used to manuallyactivate fans to rotate or translate load 130.

FIG. 14 schematically illustrates operational components of a suspendedload control system (“SLCS”) 1400 including suspended load controlsystem logical components 1401 and remote interface logical components1450 in accordance with one embodiment. Within suspended load controlsystem logical components 1401 are sensor suite 1405, which may includeposition sensors 1406, orientation sensors 1407, inertial sensors 1408,proximity sensors 1409, reference location sensors 1410, thrust sensors1411 (used in relation to fans), winch sensors 1412 (used in relation towinch(es) in an SLCS, such as to sense tension on winches and or alength of a winch control line payed out from or wound up on a winch),and cameras. Some or a portion or components of sensors 1405 may bephysically located outside of electronics box 165, such as at a locationwhere a sensed condition occurs.

SLCS processing capacity or processor 1420 includes, for example, acomputer processor and or microcontrollers. SLCS memory 1425 generallycomprises a random-access memory (“RAM”) and permanent non-transitorymass storage device, such as a solid-state drive, and contains, forexample, navigation systems 1426, target data 1427, mode or commandstate information 1428, and software or firmware code, instructions, orlogic for one or more of operational module 1500 and suspended loadcontrol decision and thrust control module 1600. Communication systems1430 include wireless systems 1431 such as a wireless transceiver andwired systems 1432. SLCS output 1415 includes thrust control 1416 andtension control 1417 via, for example, power controllers and or ESCs.Power managing systems 1440 regulate and distribute the power supplyfrom, e.g., batteries or power from a crane or other carrier. A data buscouples the various internal systems and logical components of loadcontrol system logical components 1401.

An interactive display, interactive control, remote pendant, positionalunit, or target node, all of which may also be referred to herein as“remote interface”, may be a computational unit comprising one or moreof remote interface logical components 1450; such a unit may beself-powered or hardwired into another device, such as an airframe,carrier, a remote pendant (an embodiment of which is illustrated inFIGS. 13A through 13C), a tablet computer, or the like. Remote interfacelogical components 1450 may receive data from and/or send data to theSLCS, e.g., through wireless or wireline conduits and communicationsystems. Data from the SLCS may be displayed or communicated on or viadisplay 1461 of remote interface logical components 1450; the data maybe parsed and converted to auditory, tactile, or visual cues. Remoteinterface logical components 1450 may also communicate to the SLCS theoperator's desired command states and operational instructions, asdiscussed below.

Remote interface logical components 1450 may be in communication withload control system logical components 1401 via communication systems1470, which may be wireless 1471 or wired 1472. Output 1460 from remoteinterface logical components 1450 may include information displayed on ascreen or display 1461, and auditory cues or access to remote audio(such as audio detected by sensors in a load) via audio output 1462.Output 1460 may also output tactile cues. Input 1465 to remote interfacelogical components 1450 to control an SLCS may include commands througha touchscreen 1466 or a joystick 1467, including, for example withreference to FIGS. 13A through 13C, through activation controller 240,on/off switch 245, state selector 250, and manual/rotational control251. In embodiments, manual/rotational control 251 may activate fans onopposite sides of SLCS, to produce, for example, a rotational force ortorque on load 130. In embodiments, additional control(s) may beprovided to, for example, activate fans on a same side of SLCS toproduce, for example, a translational force on load 130. In embodiments,additional control(s) may be provided to, for example, activate one ormore winches to tighten control lines. In various embodiments, remoteinterface logical components 1450 may comprise one or more physicaland/or logical devices that collectively provide the functionalitiesdescribed herein.

Aspects of the system may be embodied in a specialized or specialpurpose computing device or data processor that is specificallyprogrammed, configured, or constructed to perform one or more of thecomputer-executable instructions explained in detail herein, inconjunction with suitable memory. Aspects of the system may also bepracticed in distributed computing environments where tasks or modulesare performed by remote processing devices and memory that are linkedthrough a communications network, such as a local area network (LAN),wide area network (WAN), or the Internet. In a distributed computingenvironment, modules may be located in both local and remote memorystorage devices. As schematically illustrated in FIG. 14, load controlsystem logical components 1401 and remote interface logical components1450 may be coupled by a wired or wireless network.

Load control system logical components 1401 may work with a remotepositional unit, remote interface, or target node comprising one or moreremote interface logical components 1450, in accordance with oneembodiment. The remote positional unit, remote interface, or target nodemay comprise an internal or external sensor suite, such as sensors 1468,configured to communicate, such as wirelessly, with load control systemlogical components 1401 as a positional reference. Sensors 1468 may besimilar to or a subset of sensors 1405. If sensors 1405 are consideredthe primary sensor suite, a secondary sensor suite location may be inthe platform, crane, aircraft, or other carrier from which main loadbearing line 125 is suspended, and a tertiary sensor suite location maybe a location of interest for the load (e.g., for positioning to obtainor deliver the load). Remote interface logical components 1450 mayfurther comprise processor 1469 and memory 1473, which may be similar toprocessor 1420 and memory 1425. Memory 1473 may comprise software orfirmware code, instructions, or logic for one or more modules used bythe remote positional unit, remote interface, target node, or remoteinterface, such as remote interface module 1474. For example, remoteinterface module 1474 may provide control and interface (e.g.input/output) for a remote positional unit, remote interface, targetnode, or remote interface, such as to allow it to be turned on/off, topair it with an SLCS, to input instructions, or the like.

A remote positional unit or remote interface may include a transceiverconfigured to communicate with load control system logical components1401 via a wireless transceiver and provide a positional reference. Forexample, a remote positional unit or remote interface may be secured toa helicopter ownship, crane, or other carrier 124 below which a load maybe suspended. The remote positional unit, remote interface, or targetnode may be secured to, e.g., the helicopter, crane, or carrier bymagnets, bolts, or any other securement mechanism. The remote positionalunit, remote interface, or target node may be placed or dropped to alocation on the ground or secured to, e.g., a life preserver or otherflotational device, a rescuer, a load to be picked up, a location for aload to be delivered, or an operational specific location.

In some embodiments, the remote positional unit, remote interface, ortarget node may be made of durable polymer or plastic, large enough tofit into a hand. The remote positional unit, remote interface, or targetnode may have an external antenna.

Aspects of the load control system logical components 1401 and/or remoteinterface logical components 1450 may be embodied in a specialized orspecial purpose computing device or data processor that is specificallyprogrammed, configured, or constructed to perform one or more of thecomputer-executable instructions explained in detail herein. Aspects ofthe load control system logical components 1401 and/or remote interfacelogical components 1450 may also be practiced in distributed computingenvironments where tasks or modules are performed by remote processingdevices that are linked through a communications network, such as alocal area network (LAN), wide area network (WAN), or the Internet. In adistributed computing environment, modules may be located in both localand remote memory storage devices. As schematically illustrated in FIG.14, load control system logical components 1401 and remote interfacelogical components 1450 may be coupled by a wired or wireless network.

FIG. 15 illustrates an example of operational module 1500 of a suspendedload control system (“SLCS”) including multiple mode or command statemodules in accordance with one embodiment. Instructions of, or whichembody, decision and operational module 1500 may be stored in, forexample, memory 1425, and may be executed or performed by, for example,processor 1420, as well as by electrical circuits, firmware, and othercomputer and logical hardware of SLCS with which operational module 1500may interact. In embodiments, computer processors and memory to performsome or all of operational module 1500 may be remote from SLCS, such asin an auxiliary computer in, for example, a carrier.

In block 1505, a suspended load control system apparatus may beinstalled onto a load and/or onto a cable from which a load will besuspended. The suspended load control system apparatus need not bepowered on for installation.

In block 1510, the suspended load control system (“SLCS”) in theapparatus may be started up and operational module 1500 activated. Insome embodiments, operational module 1500 may be initialized by press ofa button located on the SLCS, such as on electronics box 165 and/orremote pendant 235. Near an external button which may initializeoperational module 1500, another button may be present that allows forimmediate shut down when pressed. In addition to the initializationinterface on the center or control module, operational module 1500 mayalso be initialized by an operator not directly next to the system. Oneor more external operators, including but not limited to an operator ofa crane or another carrier, a rescuer on the end of the cable, or thelike, may initialize operational module 1500 by pressing a button on oneor more remote interface linked wirelessly to operational module 1500.One or more modules of a complete SLCS, such as physically separatedcontrol unit, fan unit, and the like, may be started up in block 1510and may be paired to function together. During block 1510, operationalmodule 1500 may determine a relative orientation of fan units or wincheswhich operational module 1500 is to control. This determination may bebased on sensor information from the fan units or winches, such as acompass heading sampled from sensor(s) of or associated with each fanunit or winch. This determination may be performed to adjust for fanunits or winches which are not available and or which do not have afixed physical relationship, as may be the case when components of amodular SLCS are deployed on an irregular load, such as a rope orwebbing enclosed load, and the fan units or winches may not be parallelor may not have a pre-determined, fixed, physical arrangement. Thisdetermination may be used in block 1635 of FIG. 16, with respect to fanand winch mapping. This determination may not be necessary when the SLCSis in a rigid frame and the fan units or winches may be presumed to beparallel to one another. This determination may produce an errorcondition if the fan units or winches are not within an acceptableorientation range or if they are unavailable.

In block 1515, operational module 1500 may be activated. In block 1515,operational module 1500 may tension one or more winch control lines,such as by activation of winches. Operational module 1500 may sense atension on one or more winch control lines and or a length of one ormore control line, such as with winch 1412 sensors. Operational module1500 may output information regarding tension on and or length ofcontrol lines to, for example, remote interface logical components.Operational module 1500 may determine that an error condition hasoccurred, such as a winch with insufficient or too much tension, withinsufficient or too much winch control line payed out to or from awinch, or the like. An error condition may result in a report to anoperator, such as to a remote interface; an error condition may beover-ridden by a command from an operator, such as from a remoteinterface; an error condition may result in operational module 1500 notproceeding until the error condition is addressed. An error conditionmay be addressed by an operator re-securing winch control lines andre-initializing or continuing initialization of operational module 1500.

If no error condition or the like in block 1515, in block 1520, afunctional mode or command state of operational module 1500 may becalled, such as by input from an operator or another process.Maintenance of winch control line tension and absence of an errorcondition may be a condition to continuation of performance of block1520. In block 1520, operational module 1500 perform or call suspendedload control decision and thrust control module 1600 as a subroutine orsubmodule, to implement a functional mode or command state. Thefunctional modes or command states of the system may be:

Idle mode 1521: internal systems of the SLCS are operating (e.g.,operational module 1500 observes motion of the SLCS and load andcalculates corrective action), but the thrusters are shut off ormaintain an idle speed only, without action to affect the motion of theload.

Maintain relative position vs. ownship, crane, or carrier mode 1522:stabilizes the SLCS with respect to a slung origin point. For example,when SLCS is suspended with a load below a drop-point of the suspensioncable below a crane, the SLCS will stay directly below the drop-point ofthe suspension cable. Maintain relative position vs. ownship mode 1522localizes the ownship motion (including the motion of the drop-point)and performs the corrective actions necessary to critically damp anyother suspended load motion. If the ownship or drop-point is travelingat a low speed, maintain relative position vs. ownship mode 1522 willcouple the velocity or cable tension so the two entities move in unison.Upon a disturbance to the load, maintain relative position vs. ownshipmode 1522 provides thrust and or winch control line tension relative tothe direction of the disturbance to counteract the disturbance,eliminating swing.

Move to/stop at position mode 1523: will stabilize an SLCS to a fixedposition, counteracting the influence of weather or small movements ofthe crane, carrier, or other suspending platform. This mode has theeffect of killing all motion. The operator may send the desired targetposition to SLCS via a remote interface. This may be accomplished in atleast three ways:

Target node position 1524: The operator may place reference locationsensors 1468 (e.g. a positional unit or target node) at the desiredlowering location. Reference location sensors 1468 may communicatewirelessly with target node position 1524 module to indicate the desiredposition, and target node position 1524 module responds by maneuveringthe SLCS to the desired location while also adjusting winch tension toaid this maneuvering. Remote interface display 1461 may receive anddisplay the location information of both entities.

User-designated position/orientation 1525: The operator may use theremote interface display 1461 to send a designated position (e.g.,latitude and longitude coordinates) or orientation as a commandedlocation or orientation to user-designated position/orientation 1525module. The system will then steadily direct the suspended load to thedesired position or to the desired orientation. The system willsimultaneously send feedback to remote interface logical components 1450regarding position, distance, and orientation information.

Hold position or orientation mode 1526: will resist all motion of anSLCS and maintain current position and or orientation independent of theownship's motion or external forces. This module has the effect ofkilling all motion. This module has conditional responses respectivelyto ownship speed, safety factors, and physical constraints.

Direct control mode 1527: Joystick or similar operation of an SLCS inthree degrees of freedom. The operator is able to directly controlpositioning, rotation, thruster output level, or winch tension, such as,for example, using manual/rotational control 251 or another control.Though operational module 1500 is entirely closed loop and does notrequire external control during operation, there is an option for usercontrol. The operator is able to provide input to direct control mode1527 module to directly control positioning, rotation, thruster outputlevel, and winch tension.

Obstacle avoidance module 1529 module: receives and processes sensorinformation such as to i) to equalize the distance between sensorlocations, such as at fan units, and objects, such as obstacles, sensedin the environment or ii) to measure or receive geometry of a load,measure geometry of obstacles sensed in the environment, determine orreceive the position, orientation, and motion of the load, and negotiatethe load relative to the obstacle, such as through activation of fansand or winches.

In block 1530, the operator completes the operation and retrieves theSLCS.

In block 1535, operational module 1500 may be shut down by pushing abutton or the like on an interactive control, by pressing a button onthe SLCS apparatus, or the like. If the SLCS apparatus includescollapsible frame, propulsion arms, fan units, or winches, winch controllines may be reeled in, coiled, or withdrawn, arms or frame componentsmay be folded up, retracted, and the like. If the SLCS apparatusincludes removable modules, such as for fan units, winches, a housing, apower supply housing, and the like, the modules may be removed anddisassembled. The load may be detached from a load hook or the like, anda suspension cable may be detached from a hoist ring at the top of theload and/or SLCS. SLCS may then be stowed in a suitable location. Whenstowed, the SLCS may be electrically coupled to a charger or anotherpower source.

FIG. 16 illustrates a decision and thrust control module 1600 of asuspended load control system (“SLCS”) in accordance with oneembodiment. Instructions of, or which embody, decision and thrustcontrol module 1600 may be stored in, for example, memory 1425, and maybe executed or performed by, for example, processor 1420, as well as byelectrical circuits, firmware, and other computer and logical hardwareof SLCS with which decision and thrust control module 1600 may interact.In embodiments, computer processors and memory to perform some or all ofdecision and thrust control module 1600 may be remote from SLCS, such asin an auxiliary computer in, for example, a carrier, a remote interface,or the like.

Decision and thrust control module 1600 may operate in a closed loop tounderstand its position and motion in near real time, determine a mostdesired system response, and send desired response(s) to the airpropulsion system thruster array and or winches to mitigate swing of thecable or otherwise control a load during operations.

At block 1605, decision and thrust control module 1600 may obtain datafrom sensors such as, for example, sensors 1405, such as accelerometer,gyroscope, magnetometer, GPS, lidar/radar, range finders, winch sensors1412, and or machine vision input, including machine vision processingof images of winch control lines taken by cameras of an SLCS.

In block 1610, decision and thrust control module 1600 combines datafrom the sensors to obtain a data fusion describing position,orientation, motion, and environment of the SLCS apparatus.

Sensor data is fused and filtered by the SLCS through non-linear flavorsof a Kalman Filter to yield an accurate representation of the system'sstate. Closed-loop control methods including fuzzy-tuned proportional,integral, and derivative feedback controllers which may havebidirectional communication with advanced control methods including deeplearning neural nets and future propagated Kalman filters, allowing forfurther real-time system identification.

In block 1615, decision and thrust control module 1600 performs stateestimation using non-linear state estimators to project near-term futuremotion based on the data fusion and on feedback from the decision andcontrol engine to the state estimator. State estimation and near-termfuture motion may include a rate of or rate of change of rotation, amass, a center of mass, a moment of inertia, or the like; one or more ofsuch data or a change in such data may be consistent with incorrecttension of one or more winch control line.

In block 1617, decision and thrust control module 1600 receives afunctional mode selection, such as according to user input.

In block 1620, decision and thrust control module 1600 takes the stateestimation 1615, informed by the user-selected functional mode orcommand state 1617, as well as additional feedback from the thrust andorientation and winch mapping 1625 and output control 1640, anddetermines a desired direction of motion, rotation, center of mass, orresponse rate of the SLCS.

Algorithmic output is sent to motion or power controllers, such as ESCs,which will send the desired thrust response to the EDF and to thewinch(es) as winch control via, for example, phase control of pulsemodulated power signals. The net thrust output and winch control ismapped in real-time through encoders and load cells then sent back todecision and control block 1620 and onward for closed-loop control.

In block 1630, decision and thrust control module 1600 maps desiredorientation with thrust vectors from EDF to generate a thrust andorientation mapping and maps desired orientation with winch tension togenerate a winch tension mapping to achieve the determined thrust, winchtension, and orientation of the SLCS apparatus.

In block 1635, decision and thrust control module 1600 maps the thrustand orientation mapping to fans and fan thrust vectors and to winchtension vectors and generates a fan and winch mapping to control EDFsand winches to achieve the desired thrust and orientation of the SLCS.

In block 1640, decision and thrust control module 1600 applies the fanand winch mapping to output power control signals to move or exert forceas decided and to determine activation of fan(s) and or winch(es) toachieve the determined thrust and orientation of the SLCS.

In block 1640, the SLCS thrusters exert the commanded control output,implementing a dynamic response in the form of thrust and winch control,which thrust and winch control may counteract unwanted motion and or maydrive the SLCS and load in a desired manner.

If an interrupt condition occurs, such as if an incorrect winch tensionerror condition is detected or otherwise, decision and thrust controlmodule 1600 may conclude or return to a module which may have called it.

Decision and thrust control module 1600 may be unmanned and automatedaside from the high-level operator-selected functional control modes andor user input through a functional control mode. Net output is a controlforce to move, stabilize, or control a suspended load.

The entire process is unmanned and automated aside from the high-leveloperator-selected functional control modes and or user input. The netoutput is a control force to stabilize or control a suspended load.

FIG. 17A illustrates a graph of response of a suspended load tocontrolled by an SLCS, with inadequate tension on control lines. FIG.17A illustrates a graph of response of a suspended load to controlled bythe SLCS, with adequate tension on control lines, as may be producedwhen a system includes apparatuses, systems, and methods as disclosedherein. The graph with inadequate tension in FIG. 17A illustrates thatthe SLCS is oscillating around its suspended vertical axis (e.g. aboutthe Y axis). The results in reduced ability of the SLCS to control theload, increased latency in application of force (e.g. torque) from theSLCS to the load, increased power use by the SLCS, and significantlyreduced performance, which undermines the rationale for employinganother piece of equipment, e.g. the SLCS, in an operation. The graphwith adequate tension in FIG. 17B illustrates that the SLCS has reducedoscillation around its suspended vertical axis (e.g. about the Y axis),compared to the graph with inadequate tension. The results in increasedability of the SLCS to control the load, decreased latency inapplication of force (e.g. torque) from the SLCS to the load, lowerpower use by the SLCS, and performance which provides a rationale foremploying the SLCS in the operation. The graph in FIG. 17B furtherillustrates deliberate rotation the load and response of the SLCS,rather than merely trying to hold the load in one orientation, as inFIG. 17A. The graph in FIG. 17B further has a different scale than inFIG. 17A, though the significantly improved performance of the SLCS cannonetheless be seen in a comparison of these two graphs.

Status indicator lights may be mounted on various surfaces of the SLCSto aid in visibility and operation of the SLCS from above and below. Forexample, the SLCS may have external lighting such as LEDs near thethrusters that identify the edges and orientation of the SLCS. Thisallows for improved identification in hard viewing situations such asinclement weather. During operation, both on the remote interface andthe system body itself the LED display indicators show that the systemis active and convey useful information.

Electronics box 165 may contain and protect computer hardware, such as acomputer processor and memory, a power supply, electronic speedcontrollers, microcontrollers, sensors, and the like. The power supplymay be a single power brick or an array of battery cells wired in seriesand/or in parallel, such as lithium-polymer (LiPo) cells. The batteriesmay be removable for inspection and/or to swap discharged and chargedbatteries. Batteries ay be charged while installed in the SLCS (i.e.,without having to remove them) via nodes or a wireless charging systemon or in an SLCS that connect to a charging dock or power via a wirelineconnection, such as main power conduit 180. Batteries may includeauxiliary battery(ies) to supply a steady supply of power to theprocessor even if thrusters in fan units draw a relatively large amountof power from main batteries. In embodiments, the crane can provide somepower to the SLCS, while the SLCS may obtain other power from anon-board power supply. In various embodiments, the SLCS may be poweredby a combination of on-board and remote power. In many environments, allpower for the SLCS is contained on board, allowing fully autonomousoperation without dependence on the availability of external powersources or delivery means.

Contained within electronics box 165 may be a data link which allows amicrocontroller unit or processor to monitor power information including(but not limited to) cell voltage and real-time power dissipation orconsumption.

Contained within electronics box 165 may be a thruster controller toallow a computer processor to control the speed, power draw, and thrustof thrusters in the EDF. The thruster controller may be, e.g., anelectronic speed controller (“ESC”) for an EDF. An ESC typically has atleast three connections: to the power supply, to a thruster, and to theprocessor or a microcontroller, or both. The ESC pulls power from thepower supply and allocates it to the thrusters to control the amount ofthrust produced by the EDF.

Contained within electronics box 165 may be a computer processor orcentral processing unit (CPU). The processor may be an embedded systemincluding a signal board computer and one or more microcontroller units(“MCUs”). The CPU and MCUs may be contained within a housing in whichdata link connections may be made. Electronics box 165 may be made of orcomprise a rugged plastic or polymer, protecting the system fromenvironmental and operational factors such as weather and otheroperational conditions. In some embodiments, the CPU and MCUs aremounted to the same printed circuit board (PCB).

Electronics box 165 may contain one or more wireless transceivers, whichmay comprise separate transmitter(s) and receiver(s), as well asantennas for wireless communication. The transceiver and/or wirelessantennas may also be mounted to or printed on the same printed circuitboard as the processor. The wireless transceivers may comprise accesspoints for Bluetooth, Wi-Fi, microwave, and/or radio frequency (RF)transmission and reception. Wireless transceivers may be used tocommunicate with remote sensors, a remote control unit, a remotepositional unit or target node, a remote interface, and the like, asdiscussed further herein.

Electronics box 165 may contain a vector navigation unit, which mayinclude an inertial measurement unit (“IMU”). The IMU provides inertialnavigation data to the processor.

SLCS 105 may comprise or be communicatively coupled to one or moresensors in addition to the IMU. Such additional sensors may comprise,for example, an inertial measurement system, an orientation measurementsystem, and an absolute position measurement system. The inertialmeasurement system (“IMS”) may include 3 degrees of freedom (3DOF)accelerometers, gyroscopes, and gravitational sensors, which maycomprise microelectromechanical systems (MEMS) sensors. The orientationmeasurement system may include a magnometer or magnetometer such as acompass, an inclinometer, a directional encoder, and a radio frequencyrelative bearing system. The absolute position measurement system mayinclude global positioning system (GPS) sensors.

Sensors may further comprise a proximity sensor or light detection andranging (LIDAR) system (e.g., rotating or linear), and/or an opticalsensor such as one or more cameras or infrared (IR) sensors. Proximitysensors may include ground height sensors. Optical sensors can alsoprovide visual information to a user. This information may becommunicated to remote devices by the SLCS processor, via a data linkcable and/or the wireless transceiver. Proximity and optical sensorsallow the system to be capable of 360 degree awareness and collisionavoidance by detecting obstacles and altering the course of the SLCS toavoid the obstacles. The system is also capable of providing ground (orwater) position data to crane operators and ground crew. Sensors whichrequire a view of a surrounding environment may be placed on or at thesurface of SLCS 105 and/or remote from SLCS 105.

Additional SLCS sensors may include a strain sensor to gauge load onhousings, on fan unit(s), on conduits, on a securement structure to asuspension cable, a control line 110, or the like. Additional sensorsmay include a rotational encoder or thruster speed sensor which may beincremental or absolute, and a shutdown pin presence sensor.

SLCS may use remote positional sensors or beacons, remote computationalunits, or target node transceiver devices to assist in characterizingthe location and/or motion of the suspending load and/or SLCS 105 (e.g.,relative to a crane), the carrier, and a target location of interestsuch as a load destination.

The SLCS processor applies algorithms to received sensor system data toyield a desired system response. For example, GPS sensor data may berefined through real-time kinetic (RTK) algorithms to develop a refinedabsolute position. The measurements may be fused together throughnon-linear data fusion methods, such as Kalman filtration methods, toyield optimal state estimates in all degrees of freedom to characterizethe system's location and motion in geodetic space.

The apparatuses and methods in this disclosure are described in thepreceding on the basis of several preferred embodiments. Differentaspects of different variants are considered to be described incombination with each other such that all combinations that upon readingby a skilled person in the field on the basis of this document may beregarded as being read within the concept of the disclosure. Thepreferred embodiments do not limit the extent of protection of thisdocument.

Embodiments of the operations described herein may be implemented in acomputer-readable storage device having stored thereon instructions thatwhen executed by one or more processors perform the methods. Theprocessor may include, for example, a processing unit and/orprogrammable circuitry. The storage device may include a machinereadable storage device including any type of tangible, non-transitorystorage device, for example, any type of disk including floppy disks,optical disks, compact disk read-only memories (CD-ROMs), compact diskrewritables (CD-RWs), and magneto-optical disks, semiconductor devicessuch as read-only memories (ROMs), random access memories (RAMs) such asdynamic and static RAMs, erasable programmable read-only memories(EPROMs), electrically erasable programmable read-only memories(EEPROMs), flash memories, magnetic or optical cards, or any type ofstorage devices suitable for storing electronic instructions. USB(Universal serial bus) may comply or be compatible with Universal SerialBus Specification, Revision 2.0, published by the Universal Serial Busorganization, Apr. 27, 2000, and/or later versions of thisspecification, for example, Universal Serial Bus Specification, Revision3.1, published Jul. 26, 2013. PCIe may comply or be compatible with PCIExpress 3.0 Base specification, Revision 3.0, published by PeripheralComponent Interconnect Special Interest Group (PCI-SIG), November 2010,and/or later and/or related versions of this specification.

As used in any embodiment herein, the term “logic” may refer to thelogic of the instructions of an app, software, and/or firmware, and/orthe logic embodied into a programmable circuitry by a configuration bitstream, to perform any of the aforementioned operations. Software may beembodied as a software package, code, instructions, instruction setsand/or data recorded on non-transitory computer readable storage medium.Firmware may be embodied as code, instructions or instruction setsand/or data that are hard-coded (e.g., nonvolatile) in memory devices.

“Circuitry”, as used in any embodiment herein, may comprise, forexample, singly or in any combination, hardwired circuitry, programmablecircuitry such as FPGA. The logic may, collectively or individually, beembodied as circuitry that forms part of a larger system, for example,an integrated circuit (IC), an application-specific integrated circuit(ASIC), a system on-chip (SoC), desktop computers, laptop computers,tablet computers, servers, smart phones, etc.

In some embodiments, a hardware description language (HDL) may be usedto specify circuit and/or logic implementation(s) for the various logicand/or circuitry described herein. For example, in one embodiment thehardware description language may comply or be compatible with a veryhigh speed integrated circuits (VHSIC) hardware description language(VHDL) that may enable semiconductor fabrication of one or more circuitsand/or logic described herein. The VHDL may comply or be compatible withIEEE Standard 1076-1987, IEEE Standard 1076.2, IEEE1076.1, IEEE Draft3.0 of VHDL-2006, IEEE Draft 4.0 of VHDL-2008 and/or other versions ofthe IEEE VHDL standards and/or other hardware description standards.

As used herein, the term “module” (or “logic”) may refer to, be part of,or include an Application Specific Integrated Circuit (ASIC), a Systemon a Chip (SoC), an electronic circuit, a programmed programmablecircuit (such as, Field Programmable Gate Array (FPGA)), a processor(shared, dedicated, or group) and/or memory (shared, dedicated, orgroup) or in another computer hardware component or device that executeone or more software or firmware programs having executable machineinstructions (generated from an assembler and/or a compiler) or acombination, a combinational logic circuit, and/or other suitablecomponents with logic that provide the described functionality. Modulesmay be distinct and independent components integrated by sharing orpassing data, or the modules may be subcomponents of a single module, orbe split among several modules. The components may be processes runningon, or implemented on, a single compute node or distributed among aplurality of compute nodes running in parallel, concurrently,sequentially or a combination, as described more fully in conjunctionwith the flow diagrams in the figures.

As used herein, a process corresponds to an instance of a program, e.g.,an application program, executing on a processor and a threadcorresponds to a portion of the process. A processor may include one ormore execution core(s). The processor may be configured as one or moresocket(s) that may each include one or more execution core(s).

As used herein “releasable”, “connect”, “connected”, “connectable”,“disconnect”, “disconnected,” and “disconnectable” refers to two or morestructures which may be connected or disconnected, generally without theuse of tools (examples of tools including screwdrivers, pliers, drills,saws, welding machines, torches, irons, and other heat sources) or withthe use of tools but in a repeatable manner (such as through the use ofnuts and bolts or screws). As used herein, “attach,” “attached,” or“attachable” refers to two or more structures or components which areattached through the use of tools or chemical or physical bonding, butwherein the structures or components may not generally be released orre-attached in a repeatable manner. As used herein, “secure,” “secured,”or “securable” refers to two or more structures or components which areconnected or attached.

SLCS 105 may be formed of any suitable material such as metal, plastic,composite materials, such as fiber reinforced resin. SLCS 105 may allowaccess into internal space via a sealed hatch or one or more removablepanels, allowing for maintenance and inspection.

Although specific embodiments have been illustrated and describedherein, it will be appreciated by those of ordinary skill in the artthat alternate and/or equivalent implementations may be substituted forthe specific embodiments shown and described without departing from thescope of the present disclosure. For example, although variousembodiments are described above in terms of a crane, in otherembodiments an SLCS may be employed under a helicopter. This applicationis intended to cover any adaptations or variations of the embodimentsdiscussed herein.

Following are non-limiting examples.

Example 1. A load control system to influence at least one of aposition, orientation, or motion of a load suspended by a main loadbearing line from a carrier, comprising: a rotational coupling, a winch,a winch control line to be secured to the load and the winch, athruster, a sensor suite, and a computer processor and a memory; whereinthe memory comprises a control module which, when executed by thecomputer processor, is to determine a tension on the winch and at leastone of a position, orientation, or motion of the load based on a sensordata from the sensor suite and is to control the tension on the winchand the thruster to influence at least one of the position, orientation,or motion of the load, and wherein the rotational coupling is to allowthe load control system to rotate about a vertical axis of the main loadbearing line without imparting a significant torque on the main loadbearing line.

Example 2. The load control system according to Example 1, wherein theload control system is to be secured to a head block by the rotationalcoupling, wherein the head block is to be secured to the main loadbearing line.

Example 3. The load control system according to Example 1, wherein therotational coupling comprises a bearing set, wherein the bearing set isradially arrayed around a central axis of the main load bearing line.

Example 4. The load control system according to Example 1, wherein therotational coupling is not to transfer a main lifting force between thecarrier and the load and is to transfer a torque from the load controlsystem to the load via the winch control line.

Example 5. The load control system according to Example 1, wherein thewinch control line is not to transfer a main lifting force between thecarrier and the load and is to transfer a torque from the load controlsystem to the load via the winch control line.

Example 6. The load control system according to Example 1, wherein themain load bearing line comprises a load bearing rotational coupling,wherein the load bearing rotational coupling is to allow the load torotate about the vertical axis of the main load bearing line withoutimparting a significant torque on the main load bearing line.

Example 7. The load control system according to Example 1, furthercomprising at least one of a plurality of thrusters, a plurality ofwinches, a plurality of winch control lines.

Example 8. The load control system according to Example 1, wherein thethrust control module is to determine at least the position,orientation, or motion by combining the sensor data from the sensorsuite through a non-linear filter to determine a current state andwherein the control module is further to use the current state tocontrol the tension on the winch and the thruster to influence at leastone of the position, orientation, or motion of the load.

Example 9. The load control system according to Example 8, wherein touse the current state to control the tension on the winch and thethruster to influence at least one of the position, orientation, ormotion of the load is to project near-term future motion based on thecurrent state with feedback from at least one of a functional mode orcommand state of an operational module, a thrust and orientationmapping, or a fan mapping.

Example 10. The load control system according to Example 1, wherein thethruster comprise at least one of a fan or a flywheel.

Example 11. A computer implemented method to influence at least one of aposition, orientation, or motion of a load suspended by a main loadbearing line from a carrier, comprising: determining a position,orientation, or motion of the load and a tension on a winch based on asensor data from a sensor suite, wherein the winch is secured to theload with a winch control line, and controlling the winch and a thrusterto influence at least one of the position, orientation, or motion of theload, wherein a rotational coupling allows the winch and thruster torotate about a vertical axis of the main load bearing line withoutimparting a significant torque on the main load bearing line.

Example 12. The method according to Example 11, further comprisingtensioning the winch control line and activating the thruster toinfluence at least one of the position, orientation, or motion of theload.

Example 13. The method according to Example 11, further comprisingtransferring a torque from the load control system to the load via thewinch control line.

Example 14. The method according to Example 11, further comprisingtransferring a main lifting force between the load and the carrier,wherein the main lifting force between the load and the carrier bypassesthe rotational coupling.

Example 15. The method according to Example 11, wherein a load bearingrotational coupling allows the load to rotate about the vertical axis ofthe main load bearing line without imparting a significant torque on themain load bearing line.

Example 16. The method according to Example 11, further comprisingdetermining the position, orientation, or motion and the tension on thewinch by combining the sensor data from the sensor suite through anon-linear filter to determine a current state, wherein the currentstate comprises the position, orientation, or motion and the tension onthe winch.

Example 17. The method according to Example 16, further comprisingprojecting near-term future motion based on the current state andcontrolling the winch and the thruster based on the near-term futuremotion.

Example 18. The method according to Example 11, wherein projectingnear-term future motion based on the current state comprises updatingthe current state with feedback from at least one of a functional modeor command state of an operational module, a thrust and orientationmapping, a fan mapping, or a winch mapping.

Example 19. An apparatus to influence at least one of a position,orientation, or motion of a load suspended by a main load bearing linefrom a carrier, comprising: means to determine a position, orientation,or motion of the load and a tension on a winch from a winch control linebased on a sensor data from a sensor suite, means to secure the winch tothe load with a winch control line, means to control the winch, winchcontrol line, and a thruster to influence at least one of the position,orientation, or motion of the load, means for a rotational coupling,wherein the rotational coupling allows the winch and thruster to rotateabout a vertical axis of the main load bearing line without imparting asignificant torque on the main load bearing line.

Example 20. The apparatus according to Example 19, further comprisingmeans to tension the winch control line with the winch and means toactivate the thruster to influence at least one of the position,orientation, or motion of the load.

Example 21. The apparatus according to Example 19, further comprisingmeans to transfer a torque to the load via the winch control line.

Example 22. The apparatus according to Example 19, further comprisingmeans to transfer a main lifting force between the load and the carrier,wherein the main lifting force between the load and the carrier bypassesthe rotational coupling.

Example 23. The apparatus according to Example 19, further comprisingmeans for a load bearing rotational coupling to allow the load to rotateabout the vertical axis of the main load bearing line without impartinga significant torque on the main load bearing line.

Example 24. The apparatus according to Example 19, further comprisingmeans to determine the position, orientation, or motion and the tensionon the winch by combining the sensor data from the sensor suite througha non-linear filter to determine a current state, wherein the currentstate comprises the position, orientation, or motion and the tension onthe winch.

Example 25. The apparatus according to Example 24, further comprisingmeans to project near-term future motion based on the current state andmeans to control the winch and the thruster based on the near-termfuture motion.

Example 26. The apparatus according to Example 19, wherein means toproject near-term future motion based on the current state comprisesmeans to update the current state with feedback from at least one of afunctional mode or command state of an operational module, a thrust andorientation mapping, a fan mapping, or a winch mapping.

Example 27. The apparatus according to Example 19, wherein the apparatusis to be suspended above the load at a terminus of the main load bearingline.

Example 28. One or more computer-readable media comprising instructionsthat cause a computer device, in response to execution of theinstructions by a processor of the computer device, to: determine aposition, orientation, or motion of a load and a tension on a winch froma winch control line based on a sensor data from a sensor suite; controlthe winch, winch control line, and a thruster to influence at least oneof the position, orientation, or motion of the load; wherein thecomputer device is secured to a main load bearing line below a carrierby a rotational coupling, wherein the rotational coupling allows thecomputer device, winch, and thruster to rotate about a vertical axis ofthe main load bearing line without imparting a significant torque on themain load bearing line.

Example 29. The computer-readable media according to Example 28, whereinthe instructions further cause the computer device to tension the winchcontrol line with the winch and to activate the thruster to influence atleast one of the position, orientation, or motion of the load.

Example 30. The computer-readable media according to Example 28, whereinthe instructions further cause the computer device to transfer a torqueto the load via the winch control line.

Example 31. The computer-readable media according to Example 28, whereina main lifting force is transferred between the load and the carrier,wherein the main lifting force between the load and the carrier bypassesthe rotational coupling.

Example 32. The computer-readable media according to Example 28, whereinthe instructions further cause the computer device to determine theposition, orientation, or motion and the tension on the winch bycombining the sensor data from the sensor suite through a non-linearfilter to determine a current state, wherein the current state comprisesthe position, orientation, or motion and the tension on the winch.

Example 33. The computer-readable media according to Example 28, whereinthe instructions further cause the computer device to project near-termfuture motion based on the current state and means to control the winchand the thruster based on the near-term future motion.

Example 34. The computer-readable media according to Example 28, whereinthe instructions further cause the computer device to project near-termfuture motion based on the current state comprises means to update thecurrent state with feedback from at least one of a functional mode orcommand state of an operational module, a thrust and orientationmapping, a fan mapping, or a winch mapping.

1. A load control system to influence at least one of a position,orientation, or motion of a load suspended by a main load bearing linefrom a carrier, comprising: a rotational coupling, a winch, a winchcontrol line to be secured to the load and the winch, a thruster, asensor suite, and a computer processor and a memory; wherein the memorycomprises a control module which, when executed by the computerprocessor, is to determine a tension on the winch and at least one of aposition, orientation, or motion of the load based on a sensor data fromthe sensor suite and is to control the tension on the winch and thethruster to influence at least one of the position, orientation, ormotion of the load, and wherein the rotational coupling is to allow theload control system to rotate about a vertical axis of the main loadbearing line without imparting a significant torque on the main loadbearing line and wherein the thrust control module is to determine atleast the position, orientation, or motion by combining the sensor datafrom the sensor suite through a non-linear filter to determine a currentstate and wherein the control module is further to use the current stateto control the tension on the winch and the thruster to influence atleast one of the position, orientation, or motion of the load.
 2. Theload control system according to claim 1, wherein the load controlsystem is to be secured to a head block by the rotational coupling,wherein the head block is to be secured to the main load bearing line.3. The load control system according to claim 1, wherein the rotationalcoupling comprises a bearing set, wherein the bearing set is radiallyarrayed around a central axis of the main load bearing line.
 4. The loadcontrol system according to claim 1, wherein the main load bearing linecomprises a load bearing rotational coupling, wherein the load bearingrotational coupling is to allow the load to rotate about the verticalaxis of the main load bearing line without imparting a significanttorque on the main load bearing line.
 5. (canceled)
 6. The load controlsystem according to claim 1, wherein to use the current state to controlthe tension on the winch and the thruster to influence at least one ofthe position, orientation, or motion of the load is to project near-termfuture motion based on the current state with feedback from at least oneof a functional mode or command state of an operational module, a thrustand orientation mapping, or a fan mapping.
 7. The load control systemaccording to claim 1, wherein the thruster comprise at least one of afan or a flywheel.
 8. A computer implemented method to influence atleast one of a position, orientation, or motion of a load suspended by amain load bearing line from a carrier, comprising: determining aposition, orientation, or motion of the load and a tension on a winchbased on a sensor data from a sensor suite, wherein the winch is securedto the load with a winch control line, and controlling the winch and athruster to influence at least one of the position, orientation, ormotion of the load, wherein a rotational coupling allows the winch andthruster to rotate about a vertical axis of the main load bearing linewithout imparting a significant torque on the main load bearing line,further comprising determining the position, orientation, or motion andthe tension on the winch by combining the sensor data from the sensorsuite through a non-linear filter to determine a current state, whereinthe current state comprises the position, orientation, or motion and thetension on the winch.
 9. The method according to claim 8, furthercomprising tensioning the winch control line and activating the thrusterto influence at least one of the position, orientation, or motion of theload.
 10. The method according to claim 8, further comprisingtransferring a torque from the load control system to the load via thewinch control line.
 11. (canceled)
 12. The method according to claim 8,further comprising projecting near-term future motion based on thecurrent state and controlling the winch and the thruster based on thenear-term future motion.
 13. The method according to claim 12, whereinprojecting near-term future motion based on the current state comprisesupdating the current state with feedback from at least one of afunctional mode or command state of an operational module, a thrust andorientation mapping, a fan mapping, or a winch mapping.
 14. An apparatusto influence at least one of a position, orientation, or motion of aload suspended by a main load bearing line from a carrier, comprising:means to determine a position, orientation, or motion of the load and atension on a winch from a winch control line based on a sensor data froma sensor suite, means to secure the winch to the load with a winchcontrol line, means to control the winch, winch control line, and athruster to influence at least one of the position, orientation, ormotion of the load, means for a rotational coupling, wherein therotational coupling allows the winch and thruster to rotate about avertical axis of the main load bearing line without imparting asignificant torque on the main load bearing line, further comprisingmeans to determine the position, orientation, or motion and the tensionon the winch by combining the sensor data from the sensor suite througha non-linear filter to determine a current state, wherein the currentstate comprises the position, orientation, or motion and the tension onthe winch.
 15. The apparatus according to claim 14, further comprisingmeans to tension the winch control line with the winch and means toactivate the thruster to influence at least one of the position,orientation, or motion of the load.
 16. The apparatus according to claim14, further comprising means to transfer a torque to the load via thewinch control line.
 17. The apparatus according to claim 14, furthercomprising means for a load bearing rotational coupling to allow theload to rotate about the vertical axis of the main load bearing linewithout imparting a significant torque on the main load bearing line.18. (canceled)
 19. The apparatus according to claim 14, furthercomprising means to project near-term future motion based on the currentstate and means to control the winch and the thruster based on thenear-term future motion.
 20. The apparatus according to claim 19,wherein means to project near-term future motion based on the currentstate comprises means to update the current state with feedback from atleast one of a functional mode or command state of an operationalmodule, a thrust and orientation mapping, a fan mapping, or a winchmapping.